Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(e548-il) EPPLER 548 AIRFOIL | Eppler E548 general aviation airfoil Max thickness 17.4% at 35.4% chord Max camber 2.2% at 26.1% chord | Remove Airfoil details Airfoil plotter |
(e63-il) E63 (4.25%) | Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord Max camber 5.3% at 50.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e548-il,e63-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e548-il | 50,000 | 9 | 13.1 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 50,000 | 5 | 10.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 100,000 | 9 | 34.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 100,000 | 5 | 38.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 200,000 | 9 | 61.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 200,000 | 5 | 63.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 500,000 | 9 | 93.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 500,000 | 5 | 90.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 9 | 117.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 50,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 50,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 100,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 100,000 | 5 | 77.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 200,000 | 9 | 112.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 200,000 | 5 | 110 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 500,000 | 9 | 176.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 500,000 | 5 | 160 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 9 | 235.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 5 | 157.7 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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